Gas turbine-engine.



A. W. H. GRIEPE.

GAS TURBINE ENGINE.

APPLICATION FILED MAY 16, 1906. 91 0,665. Patented Jan. 26, 1909.

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GAS TURBINE ENGINE.

APPLIOATION FILED MAY 16, 190B.

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A. W. H. GRIEPE.

GAS TURBINE ENGINE.

APPLICATION FILED MAY 16, 1908.

Patented Jan. 26, 1909.

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AUeUsT w; a. GRIEPE, OFNEW Yoax, N. I

Gas rimarannema.

V Specification of Letters Patent. Applicationfiled m 1c, 1908. Serial No; 4ss,a1e..

Patented J'an.'26, 1909.-

To all whom it may concern: 3

Be it known that I, AUeUsr W." H. GRIEPE, a citizen of the United States, residing at New York, in the county of New York and Stateof New York, haveinvented new and useful Im rovements in Gas Turbine- Engines, of which the following is a specification. This invention relates to engines, the object of the invention being to provide a practical construction of rotary turbine internal combustion motor embodying a circular series of combustion chambers in connection with a corresponding series of expansion chambers forming part of and carried by a rotor, and a system of valves and igniters so arranged and combined that anyv desired number of combustion chambers, 01' all of said combustion chambers, may be put into operation in accordance withthe load to which the engine is subjected.

A further object of the invention is to provide an engine of the class referred to in which the combustion and explosion cham-v bers are arranged in two series with the chambers thereof staggered relatively to each other, thereby insuring the reliable starting of the engine and imparting to such-. engine' smooth and'(evenrunningqualitis., I

With the above and other objects in view, the nature of which will-morefnlly appear as the description proceeds, the invention consists in the novel construction, combination and arrangement of parts, herein described, illustratedand claimed.

In the accompanying d'awing'si Figure 1 is an end elevation of a complete gas turbine unit embodying the-present lnvention. Fig. 2 is a plan view thereof. Fig. 3 is 'a front .elevation, of the same. Fig. 4 is a vertical transverse section through thetu'rbine on an enlarged scale. Fig. 5 is a vertical-longitudinal section taken through oneseries of combustion and expansion chambers.

'illust'ratedin Figs. 1, 2, and 3 wherein 1 des- The general construction of the engine is ignates theturbme casing or cylinder and 2 the base thereof. 3 designates the exhaust chamber, 4 the exhaust connection leading "from the exhaust port 5 of the engine into the exhaust chamber 3, and 6 the exhaust pipe which leads out of the op osite end of the exby a system of cooling pipes (not shown).

haust chamber, the e aust gases being cooled in passing through the chamber 3 gas turbine Y 7- designates an air compressor of the retary type to which air is fed through a pipe 8 raving an inlet nozzle 9 controlled y .a valve 10. The pipe 8 may extend to and communicate with the exhaust ipe 6 and be provided with a controlling v ve 11 interposed between the air intake nozzle 9 and said exhaust pipe as shown in Fig. l for the purpose of inducing a larger suction in the exhaust tank 3. 12 designates .a compressed air accumulator to keep the air under the desired pressure regardless of irregularity of the centrifugal air compressor while from said accumulator 12 a compressed air pipe 13 leads to the turbine casing adjacent to which it is branched, the branches 14 thereof leading to opposite sides of the turbine casing to supply the two sets of airchambers thereof. 15 designates the gas or fuel tank or vaporizer in case fluid (gasolene or benzin) should be used from which a gas supply pipe 16 leads to the turbine casing, said pipe also being branched and the branches 17 thereof leading to op posite sides of the turbine casing and communicating with the different sets of gas chambers therein. inflow pipe for supplying cold water to the engine, said pipe being also branched like the other pipes and the branches 19 thereof communicating with opposite sides of the turbine casing to supply the two circulating systems of the engine. Outflow connections 18 designates the water 20 lead from opposite sides of the turbine. I

- casing to a common outflow pipe 21 to carry off the circulating Water. The compressed air pipe 13 is provided with a check valve 22 to prevent back pressure, and the water inflow pipe 18 and gas pipe 16 are provided also with check'valves 23 and 24 for alike purpose.

' The turbine casing or cylinder is made in two sections as shown in 4, the sections being flanged as shown at 25 and bolted or otherwise secured together. The outer portion of the casing forms an e ansion chamber 26 which is common tO %0l3l1 series of combustion and expansion chambers. Concentric with the outer periphery 28 of the casing is'a chambered section 29 embodying a circular series of combustion chambers 30 the outer ends of which are open and the inner endsv of which are closed with the exception of gas and air inlet ports 31.

By reference to Fig. 5 it will be seen that p the operation of the engine. I

sections 29 of the casing there is formed a 7 mg and a number of jet valves corresponding cham keep said combustion chambers cool during In each ofthe circular series of jet valve casings -34 of cylindrical form, a jet valve 35 of corre sponding shape being mounted in each caswith the number of combustion chambers as shown'in Fig. 5. Each jet valve comprises an injector nozzle 36 and a T-sha ed gas passage 37 the oppositely exten ing portions of which are adapted to register with corresponding ports 38 in the side of the casing 34, the ports 38 communicating with gas chambers 39 at opposite sides of each jet valve casing. The gas chambers 39 are arran ed a circular series as shown in Fig. 5 an within the lane of the cham bers '39 there is a circu ar series of water compartments 40 which communicate directly with each other thereby forming a practically annular water compartment interrupted only by radial spokes 41 containing radial passages 42 which communicate with an annular air chamber 43 from which the air under pressure is forced through the passages 42 and through the nozzle 36 and ports 31 into the combustion chambers 30. The sections 29 are connected by spokes 44 to the central bearings 45 in which the engine shaft 32 is journaled as shown in Figs. 4 and 5.- 46 and 47 designate circular heads or plates which are secured to opposite sides of the sections 29' 'to close in the various chambers hereinabove described.v

Each of the valves 35 is dlprovided with a stem 48 extending outwar y therefrom to a stufling box 49 in the adjacent head or plate 46 or 47 as the case may be, said valve stem being squared as shown at 50 or otherwise.

formed so that it may be turned to set the valve open or, closed by partially turning said valve either to the right or left of the position shown in Fig. 5 t us enabling any desired number of valves to be opened for the purpose of admitting the explosivemixture to the desired number of combustion chambers 30.

Mounted fast on the engine shaft 32 is a rotor' comprising a hub 51 ands okes 52 extendingoutwar from the hub etween the sections 29 of the turbine as shown in Fig. 4. The rotor carries a rim 53 projecting from opposite sides of the spokes 52 and moving in annular grooves 54 in the sections 29, sai rim-working between the valve casings 34and en is oblique with respect toa line' radial to the centrally arranged engine shaft 32, the object being to direct the lines. of explosion at corres' onding angles or in other} words in lines ob 'que to the axis of rotation! of the rotor. The section 29 also comprises water cooling s aces 33 between andaround the walls of t e combustion chambers 'to' ol est i-asshown Figs. 4 and'5. At its opposite the is provided with ports 55 coredges, responding-in location and number with the .ports 31 leadingfltq the combustion chamber "and as said rim is carried around by and with [the rotor, the.

. orts', 55 are alternately brought into an out of register with the ture simultaneously to all of the combustion chambers and also acts'as acut-off for the explosive mixture preparatory to the ignition of the chargesin'sai'd chamber. I v

. Extending laterally into each combustion chamber 30'is a spark lug 56 and all ofsaid spark plugs at both si es of the rotor are fed or energized b the rotor whic thus acts in the ca a commutator to which the secon rent of'an ignition circuit may be led 111 any convenient manner. The arrangement described provides for simultaneously sparking the mixture in all of the combustion chambers. v

The outer portion of the rotor which operates around the combustion chambers 30 embodies a circular series ofex ansion chambers 58 and intervening poc ets or spaces 59. These expansion chambers correspond in number the number of combustion chambers 30 and within each of said expansion chambers is arranged a plurality of propelling vanes 60. By reference to Fig. 5 it will be observed that the general direction of the walls of the explosion chambers and the vanes located therein is oblique to a line radial to the shaft 32 and furthermore, the line of obliquity is reversed to that of the combustion chambers 30. Therefore, the line of explosiveforceis oblique or at an angle relative to the I it'chof the propelling vanes and inner wa ls of the expansion chambers so that the impact of the expanding gases against the propelling vanes will act to impart'rotary motion to the rotor. Furthermore, it will be observed by reference to Fig. 4 that the chambers ofone series are staggered 'or arranged to alternate relatively to the chambers ofthe'seriesat the opposite side of the rotor. Thus, one series 0 acity of the inner an of thecoinbustion chainteigeo .ports 31. The rim thus acts in the capacity of'a valve common to all of the "combustion chambers for'admitting the' explosive mixcontact points 57 carried by expansion chambers is always in line with the corresponding combustion chambers, which insures-the insta'ntaneousstar'ting of the engine and renders the same smooth and 'easyin operation. It will also be seen by reference to Fig. 4 that the expansion chambers 58 have an outward flare, the effect of outer chambers 33 and thence outward through openings 62 in the head plates 46 and 47 to the water outflow branches above referred to. The gas is admitted to the chambers 39 and then enters the jet valves 35 through the ports 38 when it is taken up by the compressed air passing through the nozzles 36. This arrangement allows a change of the composition or density of the explosive mixture, then by regulating the air pressure through the air accumulator by means of a reducing valve, the mixture may be changed, allowing the same time for charging the chamber 30. A high pressure will produce a different proportion of gas and air as will a low air pressure and therefore the power of the escaping gases will be varied each of the combustion chambers being thus charged with an explosive mixture under compression.

I claim 1. A gas turbine engine embodying a stationary cylindrical turbine casing comprising a plurality of circular series of combustion chambers, a rotor encircling said series of combustion chambers and provided with a plurality of series of expansion chambers, the chambers of one series being staggered relatively to the chambers of the adjoining series, and propelling blades located in said expansion chambers.

2. A gas turbine engine comprising a stationary cylindrical turbine casing embodying a series of combustion chambers, a rotor encircling said series of combustion chambers and provided with expansion chambers having a lateral outward fiare, and propelling blades located in said expansion-chambers.

3. A gas turbine engine comprising a stationary cylindrical turbine casing comprising a circular series of combustion chambers, a corresponding series of jet valves for charging said chambers, a rotor encircling said series of combustion chambers and provided with chambers, two series of jet valves for charging the combustion chambers, and a cut-off rim carried by the rotor, said rim projecting between both series of valves and combustion chambers, and having ports therein, substantially as and for the purpose described.

5. A gas turbine engine embodying a stationary cylindrical turbine casing comprising a circular series of combustion chambers, a rotor encircling said series of combustion chambers and provided with expansion chambers, propelling blades located in said expansion chambers, means for charging said combustion chambers with an explosive mixture under pressure, means for igniting the charges, an exhaust chamber communicating with the engine casing and forming the base for the same, an exhaust pipe, a fresh air intake pipe leading to the supply pipe of the air com ressor, and means whereby said pipes may e controlled for causing the air compressor to create a suction in the exhaust chamber or derive its supply of air inde endently of the engine exhaust, substantia ly as described.

In testimony whereof I affix my signature in presence of two witnesses.

AUGUST W. H. GRIEPE.

Witnesses:

H. M. WEs'r, H. G. WOLFE. 

